Dimension-Optimizing Design Method For Annular-Type Cooling Channel Of Thrust Chamber,

Abstract

The new-generation liquid oxygen/hydrocarbon propellant liquid fuel rocket engine will use a high-pressure combustion chamber arrangement. In this case, cooling the thrust chamber becomes a key technical problem. The article presents a design scheme for the geometric-dimension optimization of annular-type regenerative cooling channels. The aim of the optimization is minimum pressure losses as coolant passes through the cooling channel. As shown in typical computations and experiments, application of this optimizing design method can reduce 50% of pressure losses. In other words, the optimization design is advantageous in solving the cooling problem in high-pressure thrust chambers. jg

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 09, 1995
Accession Number
ADA294772

Entities

People

  • Jie Chen

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chambers
  • Combustion
  • Combustion Chambers
  • Engines
  • Equations
  • Flow Rate
  • Heat Transfer
  • Heat Transfer Coefficients
  • Heat Transmission
  • High Pressure
  • Liquid Oxygen
  • Physical Properties
  • Propellants
  • Regenerative Cooling
  • Rocket Engines
  • Thermal Conductivity
  • Thrust Chambers

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Systems Analysis and Design